US20190086920A1 - Persistent surveillance unmanned aerial vehicle and launch/recovery platform system and method of using with secure communication, sensor systems, targeting systems, locating systems, and precision landing and stabilization systems - Google Patents
Persistent surveillance unmanned aerial vehicle and launch/recovery platform system and method of using with secure communication, sensor systems, targeting systems, locating systems, and precision landing and stabilization systems Download PDFInfo
- Publication number
- US20190086920A1 US20190086920A1 US15/885,152 US201815885152A US2019086920A1 US 20190086920 A1 US20190086920 A1 US 20190086920A1 US 201815885152 A US201815885152 A US 201815885152A US 2019086920 A1 US2019086920 A1 US 2019086920A1
- Authority
- US
- United States
- Prior art keywords
- recovery
- coupled
- launch
- module
- cable
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000011084 recovery Methods 0.000 title claims abstract description 121
- 238000004891 communication Methods 0.000 title claims abstract description 65
- 230000002085 persistent effect Effects 0.000 title claims abstract description 36
- 238000000034 method Methods 0.000 title claims abstract description 11
- 230000008685 targeting Effects 0.000 title abstract description 10
- 230000006641 stabilisation Effects 0.000 title abstract description 3
- 238000011105 stabilization Methods 0.000 title abstract description 3
- 239000000835 fiber Substances 0.000 claims abstract description 15
- 238000012546 transfer Methods 0.000 claims description 14
- 230000007246 mechanism Effects 0.000 claims description 13
- 239000000446 fuel Substances 0.000 claims description 12
- 230000033001 locomotion Effects 0.000 claims description 12
- 238000012360 testing method Methods 0.000 claims description 11
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 11
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims description 10
- IBSREHMXUMOFBB-JFUDTMANSA-N 5u8924t11h Chemical compound O1[C@@H](C)[C@H](O)[C@@H](OC)C[C@@H]1O[C@@H]1[C@@H](OC)C[C@H](O[C@@H]2C(=C/C[C@@H]3C[C@@H](C[C@@]4(O3)C=C[C@H](C)[C@@H](C(C)C)O4)OC(=O)[C@@H]3C=C(C)[C@@H](O)[C@H]4OC\C([C@@]34O)=C/C=C/[C@@H]2C)/C)O[C@H]1C.C1=C[C@H](C)[C@@H]([C@@H](C)CC)O[C@]11O[C@H](C\C=C(C)\[C@@H](O[C@@H]2O[C@@H](C)[C@H](O[C@@H]3O[C@@H](C)[C@H](O)[C@@H](OC)C3)[C@@H](OC)C2)[C@@H](C)\C=C\C=C/2[C@]3([C@H](C(=O)O4)C=C(C)[C@@H](O)[C@H]3OC\2)O)C[C@H]4C1 IBSREHMXUMOFBB-JFUDTMANSA-N 0.000 claims description 7
- 238000013500 data storage Methods 0.000 claims description 7
- 239000003381 stabilizer Substances 0.000 claims description 7
- 230000003287 optical effect Effects 0.000 claims description 5
- 238000012937 correction Methods 0.000 claims description 2
- 238000010304 firing Methods 0.000 claims description 2
- 230000004297 night vision Effects 0.000 claims description 2
- 238000013021 overheating Methods 0.000 claims description 2
- 210000000352 storage cell Anatomy 0.000 claims 6
- 238000001816 cooling Methods 0.000 claims 2
- 238000001228 spectrum Methods 0.000 claims 2
- 230000003213 activating effect Effects 0.000 claims 1
- 238000004873 anchoring Methods 0.000 claims 1
- 239000004570 mortar (masonry) Substances 0.000 abstract description 24
- 238000012544 monitoring process Methods 0.000 abstract description 6
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 230000007123 defense Effects 0.000 abstract description 2
- 230000004044 response Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 13
- 230000008878 coupling Effects 0.000 description 6
- 238000010168 coupling process Methods 0.000 description 6
- 238000005859 coupling reaction Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 4
- 230000010354 integration Effects 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- KJLPSBMDOIVXSN-UHFFFAOYSA-N 4-[4-[2-[4-(3,4-dicarboxyphenoxy)phenyl]propan-2-yl]phenoxy]phthalic acid Chemical compound C=1C=C(OC=2C=C(C(C(O)=O)=CC=2)C(O)=O)C=CC=1C(C)(C)C(C=C1)=CC=C1OC1=CC=C(C(O)=O)C(C(O)=O)=C1 KJLPSBMDOIVXSN-UHFFFAOYSA-N 0.000 description 1
- 239000006096 absorbing agent Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000003466 anti-cipated effect Effects 0.000 description 1
- 230000003190 augmentative effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000295 complement effect Effects 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 238000013480 data collection Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 238000009472 formulation Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000003384 imaging method Methods 0.000 description 1
- 230000010365 information processing Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 230000007257 malfunction Effects 0.000 description 1
- -1 mechanical fasteners Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000006855 networking Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 244000062645 predators Species 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000000284 resting effect Effects 0.000 description 1
- 230000002123 temporal effect Effects 0.000 description 1
- 238000001931 thermography Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
- G05D1/106—Change initiated in response to external conditions, e.g. avoidance of elevated terrain or of no-fly zones
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/0094—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots involving pointing a payload, e.g. camera, weapon, sensor, towards a fixed or moving target
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D17/00—Parachutes
- B64D17/80—Parachutes in association with aircraft, e.g. for braking thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/02—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables
- B64F1/029—Ground or aircraft-carrier-deck installations for arresting aircraft, e.g. nets or cables using a cable or tether
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F1/00—Ground or aircraft-carrier-deck installations
- B64F1/36—Other airport installations
- B64F1/362—Installations for supplying conditioned air to parked aircraft
- B64F1/364—Mobile units
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F3/00—Ground installations specially adapted for captive aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F3/00—Ground installations specially adapted for captive aircraft
- B64F3/02—Ground installations specially adapted for captive aircraft with means for supplying electricity to aircraft during flight
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
- G02B27/01—Head-up displays
- G02B27/017—Head mounted
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
- G02B27/01—Head-up displays
- G02B27/017—Head mounted
- G02B27/0172—Head mounted characterised by optical features
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
- G02B27/64—Imaging systems using optical elements for stabilisation of the lateral and angular position of the image
- G02B27/644—Imaging systems using optical elements for stabilisation of the lateral and angular position of the image compensating for large deviations, e.g. maintaining a fixed line of sight while a vehicle on which the system is mounted changes course
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/0011—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots associated with a remote control arrangement
- G05D1/0038—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots associated with a remote control arrangement by providing the operator with simple or augmented images from one or more cameras located onboard the vehicle, e.g. tele-operation
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
- G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
- G05D1/0866—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted to captive aircraft
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
- G05D1/10—Simultaneous control of position or course in three dimensions
- G05D1/101—Simultaneous control of position or course in three dimensions specially adapted for aircraft
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
- H04N23/60—Control of cameras or camera modules
- H04N23/68—Control of cameras or camera modules for stable pick-up of the scene, e.g. compensating for camera body vibrations
- H04N23/682—Vibration or motion blur correction
- H04N23/685—Vibration or motion blur correction performed by mechanical compensation
-
- H04N5/23299—
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N7/00—Television systems
- H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
- H04N7/181—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a plurality of remote sources
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N7/00—Television systems
- H04N7/18—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast
- H04N7/183—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a single remote source
- H04N7/185—Closed-circuit television [CCTV] systems, i.e. systems in which the video signal is not broadcast for receiving images from a single remote source from a mobile camera, e.g. for remote control
-
- B64C2201/027—
-
- B64C2201/042—
-
- B64C2201/06—
-
- B64C2201/123—
-
- B64C2201/127—
-
- B64C2201/141—
-
- B64C2201/148—
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/60—Tethered aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
- B64U2101/30—UAVs specially adapted for particular uses or applications for imaging, photography or videography
- B64U2101/31—UAVs specially adapted for particular uses or applications for imaging, photography or videography for surveillance
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/10—UAVs characterised by their flight controls autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2201/00—UAVs characterised by their flight controls
- B64U2201/20—Remote controls
- B64U2201/202—Remote controls using tethers for connecting to ground station
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/30—Supply or distribution of electrical power
- B64U50/34—In-flight charging
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U60/00—Undercarriages
- B64U60/50—Undercarriages with landing legs
-
- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
- G02B27/01—Head-up displays
- G02B27/0101—Head-up displays characterised by optical features
- G02B2027/0141—Head-up displays characterised by optical features characterised by the informative content of the display
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04N—PICTORIAL COMMUNICATION, e.g. TELEVISION
- H04N23/00—Cameras or camera modules comprising electronic image sensors; Control thereof
- H04N23/60—Control of cameras or camera modules
- H04N23/695—Control of camera direction for changing a field of view, e.g. pan, tilt or based on tracking of objects
Definitions
- the field of the invention relates generally to unmanned airborne surveillance systems which provide persistent surveillance capabilities in austere or remote environments that lack access to a variety of resources (e.g., fuel resources) and are in a high risk environment thus require remote deployment and in some embodiments remote recovery.
- resources e.g., fuel resources
- various embodiments of the invention include various self-contained elements along with sensor and communication capabilities including secure communication and visual sensors as well as remote targeting or geo-locating capabilities from a mobile platform with an air deployable power system.
- a deployable or portable persistent surveillance requires rapid movement and setup; ability to operate in remote environments that is, in some cases, hostile or a denied movement environment; a robust, survivable, assured network communication capability, a networked enterprise to link and synchronize various tiers or systems of sensor system employment, data accessibility, and analytic effort; an enhanced system-level analytical and information exploitation tools that fill gaps in our ability to see and understand entities and activities within a given area or environment; planning tools and control methodologies for coordinating and controlling multiple data collection, analysis and information processing systems; and an ability to detect a change in the area or environment of interest.
- Surveillance paradigms are rapidly evolving from periodic, forensic surveillance to persistent surveillance reliant on integrated systems and predictive analysis.
- persistent surveillance should capture both ongoing specific activity and, if necessary, forensically reconstruct activity after the event.
- Embodiments that are needed support a collection strategy that emphasizes an ability of some collections systems to linger on demand in an area to detect, locate, characterize, identify, track, target, and possibly provide battle damage assessment and re-targeting in real or near real time.
- Persistent surveillance facilitates the formulation and execution of preemptive activities to deter or forestall anticipated adversary courses of action.
- Various needs also include a capability supporting inclusion of synchronization and integration that reinforces operations and intelligence functions that are fully linked down to a lowest echelon and include sensors commonly associated with intelligence collection activities.
- Locate allows users to know precisely where the entity of interest is in an operational environment. Detection and location are not synonymous. Some sensors will only detect the entity then alert the system to focus its assets to precisely locate and characterize the entity. Tracking includes an ability to display or record the successive positions of a moving object in spite of natural obstacles or man-made countermeasures. This temporal requirement must be met to ensure that targets do not disappear and requires networked sensor integration and survivability. Targeting allows users to link all necessary entities or functions to address a given entity of interest or target as a mission requires which includes performance of a variety of tasks.
- Desired capabilities further include includes denial of sanctuary or ability to operate without being observed by providing persistent surveillance, tracking, and rapid engagement with high-volume precision task or application of effects. Another capability includes finding and performing tasks with respect to an entity while limiting unwanted effects such as collateral damage. Another set of desired capabilities includes developing a means to deny sanctuary to potential adversaries for a specific mission, area, and time period, support to application of long range systems to an entity of interest, extending surveillance and information collection across time, space, and information domains that is resistant to determined denial and deception efforts. Another desired need is to match a frequency of revisit with time stability of the object that a user is looking at—the speed with which things change.
- surveillance sensors are high demand/low density assets; users must prioritize and clearly define intelligence requirements and acknowledge risk in areas/objects not identified as priorities; achieved only for specific periods of time against extremely critical entities of interest; and dilutes efforts against other entities of interest priorities due to extended focus and allocation of sensors directed against one entity.
- At least some embodiments of the invention seeks to achieve real-time geo-location tracking of the activity via an aerial surveillance system that provides aerial surveillance capability to exemplary users such that they can know exactly where an activity of interest is located and provide real-time geo-location and positioning information for extremely accurate targeting of the activity of interest.
- Embodiments of this disclosure provides a user with precise targeting, without manned air assets, a base of operation that is highly mobile and allows swift relocation, and a capability to operate in a denied or hostile environment or in relatively close proximity to such an environment.
- An exemplary embodiment of the invention relates to an aerial surveillance system enabled by an aerial short wave infrared (SWIR) surveillance system platform for use in an exemplary field of operation where a quick response is preferred in reaction to real-time conditions by relaying the geo-location and other monitoring assistance via wireless or fiber SWIR optic links.
- An embodiment is capable of performance and deployment in many different conditions including any time of day (whether dark or light) and wide varieties of weather.
- Embodiments can include an aerial surveillance system that can be used in various applications such as to assist with base defenses, monitor parking lots or facilities, provide security monitoring, assist farmers planting fields, or assisting in the coordination of planting crops, or use by mortar crews in an exemplary hostile field of operation and in conjunction with mortars, e.g., the M30 mortar.
- an exemplary aerial surveillance system can be used to monitor any activity that would benefit from real-time information being relayed to the user.
- FIG. 1 shows an exemplary longitudinal view (top) and partial cross section view (bottom) of an unmanned aerial vehicle (UAV) with launch, persistent surveillance enablement, and recovery (PSER) platform system in accordance with one exemplary embodiment;
- UAV unmanned aerial vehicle
- PSER persistent surveillance enablement, and recovery
- FIG. 2 shows an alternative exemplary longitudinal view and partial cross section of the exemplary UAV with PSER platform embodiments such as shown in FIG. 1 suitable for use with a tether power cable feed from a power transfer system, e.g., cone spool;
- a power transfer system e.g., cone spool
- FIG. 3 shows an exemplary longitudinal view and partial cross section of an UAV such as in, e.g., FIG. 2 , utilized in an exemplary embodiment
- FIG. 4 shows an exemplary user optics viewing or queuing system equipment of an exemplary embodiment that displays video and data outputs from the UAV;
- FIG. 5 shows a block diagram of an exemplary system architecture in accordance with exemplary embodiments of the present disclosure
- FIG. 6 shows a longitudinal view of an airdrop system enabling autonomous navigation to a landing target for an exemplary PSER Platform System
- FIG. 7 shows an exemplary embodiment in accordance with this disclosure of an aerial surveillance system in an exemplary operational context
- FIG. 8 shows an aerial map view used in accordance with the exemplary surveillance system enabled by the present disclosure
- FIG. 9 shows a screen shield view of a user video and data display system
- FIG. 10 shows an example of laser spotting system used in relation one exemplary embodiment which would be viewable by optical systems on an exemplary UAV viewing an area which can be used as an aid in targeting;
- FIGS. 11A and 11B shows an exemplary base station/UAV recovery system and system architecture of an exemplary PSER platform in accordance with one exemplary embodiment
- FIGS. 12A and 12B shows a method of operating an exemplary embodiment of present disclosure.
- FIG. 1 a longitudinal and partial cross section view of an exemplary UAV 107 with an exemplary PSER platform system 101 is shown.
- This exemplary PSER platform system 101 includes a first section 123 and a second section 125 .
- the first section 123 and second section 125 are coupled to one another via removable coupling sections 120 , e.g., cargo straps.
- the first section 123 includes a deployable powered parachute or parafoil system (DPPPS) 103 , a propulsion system 129 (optional), and a guidance navigation system (e.g., see 323 , 5 ).
- DPPS deployable powered parachute or parafoil system
- the DPPPS 103 attaches to the first section 123 via a detachable and reattachable cable 131 , which extends from the DPPPS 103 to the second section 125 .
- An alternative embodiment can be provided that, upon landing, the DPPPS 103 retracts into a parachute storage container (e.g., see 319 , FIG. 5 ).
- a cover 115 of the second section 125 retracts, allowing for UAV 107 to be deployed from PSER platform system 101 .
- Cover 115 may be retracted or opened through any suitable mechanical system,
- the cover 115 can also be jettisoned as well including by, e.g., release mechanisms or servos (not shown) that are controlled by an onboard control system or if the cover retraction system malfunctions for example.
- the second section 125 of PSER platform system 101 includes several components of the exemplary system comprising a UAV 107 , UAV launch and recovery base system 325 , generator 119 , tether 169 , slip ring assembly 117 , feed guide motor 111 , fuel (e.g., see 114 , FIG. 5 ), and fuel storage bladder 113 .
- the second section 125 may include two separate subsections: a retrievable section 125 A and an expendable section 125 B.
- retrievable section 125 A is releasably coupled to expendable section 125 B with releasable couplers 126 (two of which are shown but releasable couplers 126 on opposing sides not shown).
- the releasable couplers 126 may be attached on each side of the second section 125 .
- the releasable couplers 126 may be attached on only one side of second section 125 up to every side of the second section 125 or any arrangement in between to include releasable couplers 126 between the two sections on an interior section or a non-side section.
- the UAV 107 in its non-deployable position, rests on UAV launch and recovery base system 325 , and may be selectively coupled to generator 119 via tether 169 .
- UAV 107 may be disposed within the retrievable section 125 A.
- Launch and recovery base system 325 holds and locks into place UAV 107 when not in use.
- Launch and recovery base system may include a UAV retainer system (not shown) which is configured to hold the UAV in place while the PSER platform system 101 is in motion.
- UAV retainer may include selectively coupling structures (e.g. servo operated clamps) that lock the UAV in place, while in other embodiments, other mechanical or electro-mechanical structures (e.g., Velcro® on the UAV landing structure and surface it rests upon) may be used to hold UAV in place to prevent damage when PSER platform system 101 is in motion.
- Slack from tether 169 may be coiled around slip ring assembly 117 until UVA 107 deploys, at which point tether 169 passes through feed guide motor 111 until fully extended.
- Feed guide motor 111 contains a reversing mechanism (e.g., see 112 , FIG. 5 ) and reels tether 169 back onto slip ring assembly 117 until UAV 107 is coupled to launch and recovery base system 325 .
- Feed guide motor 111 also keeps tension on tether 169 .
- Tether 169 connection increases flight time and prevents jamming and unfriendly or otherwise hostile control of UAV 107 .
- UAV 107 may launch to about 3000 feet vertically, depending on the terrain. This exemplary launch height provides users with range and geo-location of enemy combatants within target area (e.g., see 403 , FIG. 7 ) and prevents combatants from locating PSER platform system 101 .
- Tether 169 also may transfer power from the generator 119 to the UAV 107 .
- Generator 119 is powered by fuel (e.g., see 114 , FIG. 5 ) stored in fuel storage bladder 113 or by optional battery pack 121 , both of which are stored in the second section 125 .
- the generator 119 , fuel storage bladder 113 or optional battery pack 121 may be included in the expendable section 125 B.
- generator 119 may be disposed in the retrievable section 125 A.
- the UAV 107 may also deploy from the PSER platform system 101 in an untethered state and include its own auxiliary power source (e.g., see 173 , FIG. 3 ).
- Expendable section 125 B may by constructed to allow for safe landing at the target destination (e.g., see 381 , FIG. 6 ).
- expendable section 125 B can optionally include a mechanism configured to safely disperse the force and lessen the impact of landing on hard surfaces, such as by using wooden boards, spring-like or shock absorber mechanisms, an adjustable pressure airbag, or a crush section (not shown) to absorb kinetic energy from a hard landing.
- expendable section 125 B can optionally comprise a buoyancy system (e.g., see 321 , FIG. 5 ) allowing PSER platform system 101 to float in water. PSER platform system 101 can then be optionally guided around the water with deployed UAV 107 .
- An alternative embodiment may include an optional anchor system (e.g., see 327 , FIG. 5 ), which anchors launch barrel 101 to the bottom of a body of water. This allows for PSER platform system 101 to remain in place if UAV 107 is in its untethered state.
- Further alternative embodiments can also be provided with a drivetrain (not shown) and wheels (not shown) coupled with the expendable section 125 B and configured to be guided by personnel off-site via a remote connection.
- the exemplary PSER platform system 101 is adapted to be launched or ejected from an aircraft (e.g., see 502 , FIG. 11B ), after which the DPPPS 103 deploys and expands guiding the exemplary PSER platform system 101 to its target destination (e.g., see 381 , FIG. 6 ).
- an optional PSER platform system concealment system 134 may cover at least a portion of the PSER platform system 101 resulting in the PSER platform system 101 being camouflaged with the surrounding environment.
- PSER platform concealment system 134 may be deployed upon landing such that a force against the bottom of the second section 125 will release the PSER platform concealment system 134 to cloak or cover at least portions of the PSER platform system 101 .
- Sections of the PSER platform concealment system 134 can include camouflage, extendable sheets, etc. that can drop and unroll from a stored configuration via gravity and weights or extend from a roller controlled by a motor that roll down a guideline or track system at its edges, etc.
- the PSER platform system 101 may include a platform surveillance system (not shown).
- the surveillance system may comprise a camera to survey the environment and identify approaching threats.
- the camera may be configured to rotate 360 degrees around the PSER platform system 101 .
- a motion detector may be included in the surveillance system and configured to activate the camera once movement is detected.
- the surveillance system can be in communication with the communications system (e.g., see 163 , FIG. 3 ) or base control system 300 (shown in FIG. 5 ). For example, if surveillance system is activated, it can send a control signal or power command to a decoupler mechanism to detach the UAV 107 from PSER platform system 101 so it will not be apprehended by hostiles.
- FIG. 2 a longitudinal and partial cross-sectional view of an alternative embodiment of an exemplary PSER platform system 101 is shown.
- the tether 169 is coiled around a fiber optic spool 153 , replacing slip ring assembly (e.g., see 117 , FIG. 1 ) and feed guide motor (e.g., see 111 , FIG. 1 ), thereby reducing weight, as the fiber optic spool 153 weighs less than the slip ring assembly (e.g., see 117 , FIG. 1 ) and feed guide motor (e.g., see 111 , FIG. 1 ).
- slip ring assembly e.g., see 117 , FIG. 1
- feed guide motor e.g., see 111 , FIG. 1
- Power converter/electrical distribution 151 within the second section 125 of the PSER platform system 101 which provides power to the base control system (e.g., see 300 , FIG. 5 ), UAV 107 , and UAV flight guidance control system (e.g., see 106 , FIG. 3 ).
- releasable couplers 126 may releasably couple retrievable section 125 A to expendable section 125 B.
- UAV 107 utilized in an exemplary embodiment is shown.
- UAV 107 comprising an airframe 167 , a UAV propulsion system 161 , a primary computer system 189 , a communications system 163 , a UAV controller 165 , a photovoltaic power source 172 , landing gear 177 , a sensor system 187 , and optional gripper 211 .
- the UAV propulsion system 161 is associated with airframe 167 and comprises propellers 171 coupled to electric motors 175 , providing the lift necessary for the UAV 107 to maintain flight.
- one or more landing gears 177 stabilize the UAV 107 and provide a structure for resting UAV 107 on a surface when not in flight.
- Propellers 171 may be about ten inches in length in this embodiment. Of course, propellers 171 may be longer or shorter than ten inches, depending on the implementation.
- the UAV 107 including electric motors 175 , are powered by tether 169 when in a tethered state. However, UAV 107 , including electric motors 175 , can be powered by UAV auxiliary power source 173 .
- the auxiliary power source 173 may be, for example, an electric battery, an engine that burns liquid fuel (e.g., internal combustion engine), or a photovoltaic power source 172 powered by laser light impulses from a laser (e.g., see 181 A, FIG. 10 ).
- Auxiliary power source 173 may also be swappable to enable persistent flight of UAV 107 .
- at least one other power source e.g., tether 169
- UAV 107 is using power.
- the UAV primary computer system 189 is associated with one or more sensor systems 187 and communications systems 163 and comprises software 260 , non-volatile memory 262 , input/output ports 264 , a computer system processor 213 , GPS locator 212 , and a controller 165 .
- Sensor system 187 is configured to generate information about the environment around and below UAV 107 .
- Sensor system 187 may comprise of UAV camera 179 , UAV laser 181 B, and a gimbal stabilizer 183 to stabilize sensors, which are configured to generate information about the environment around UAV 107 or generating information for mortar team (e.g., see 401 , FIG. 7 ) such as laser pointer lines (e.g., see 409 , FIG. 8 ).
- UAV camera 179 can be, for example, a still image camera, a video camera, an infrared camera, or a multispectral camera, configured to take and record images or videos, including live feed video, and transmit images or videos to the soldier optic queuing system (e.g., see 251 , FIG. 4 ).
- the sensor system 187 may carry Light Detection and Ranging (LIDAR) 201 , sonar 204 , and traffic collision avoidance system (TCAS) 206 .
- LIDAR Light Detection and Ranging
- TCAS traffic collision avoidance system
- Data collected by the sensor system 187 may be stored on the device collecting the data (e.g., the UAV camera 179 if that camera captured that data), or the data may be stored on non-volatile memory 262 of the UAV primary computer system 189 .
- the UAV 107 may use one or more communications systems 163 , such as a communication subsystem or wired subsystem, configured to provide communications between UAV 107 and another device via wireless or wired methods.
- Communications systems 163 may comprises radio transceivers 202 , infrared devices 208 , optical ultrasonic and electromagnetic devices 210 , and ports 220 such as Ethernet ports 220 A, USB ports 220 B, serial ports 220 C, or other types of ports configured to establish a wired connection to the UAV 107 with other devices, such as a ground control station (GCS), flight planning system (FPS), or other devices, for example a mobile phone, tablet, personal computer, display monitor, other network-enabled devices.
- GCS ground control station
- FPS flight planning system
- Communications system 163 can transmit a live video feeds to mortar teams (e.g., see 401 , FIG. 7 ), signal them with UAV laser 181 B in the field, as well as send SAT PHONE/COM info from radio transceivers 202 . Additionally, the communications system 163 may optionally contain an RF signal source 185 emitted through the sensor system 187 . One or more RF signals may be detectable by an payload, and or sensor systems.
- Controller 165 associated with UAV primary computer system 189 may control operation of various systems within a UAV 107 .
- Controller 165 may have a processor unit 230 and an autopilot feature 232 along with a desired level of intelligence to aid in the operation of UAV 107 .
- Controller 165 may receive commands, tasks, or other types of information depending on the level of intelligence of controller 165 . Further, controller 165 may operate UAV 107 using optional navigation software 234 in some embodiments.
- FIG. 4 an isometric view of a helmet 255 and a frontal view of a screen shield or display 253 of the soldier optics queuing system 251 , which comprises a screen shield or display 253 , helmet 255 , camera 180 , fan ventilator 267 , battery pack 269 , and USB connection 271 .
- Screen shield or display 253 is coupled to helmet 255 via attachment lugs 257 .
- the screen shield or display 253 displays navigational 259 , status 261 , targeting 263 , and trajectory 265 data along with real-time images transmitted to screen shield or display 253 from camera 180 .
- the screen shield or display can be a semi-transparent heads up display.
- Camera 180 can include thermal imaging camera, night vision, infrared, etc.
- camera 180 can be UAV camera (e.g., see 179 , FIG. 3 ) located on UAV (e.g., see 107 , FIG. 3 ).
- helmet 255 can be replaced with any type of head mount that supports and orients solider optics queuing system 251 or configured to fit on a user's head.
- the head mount may include an elastic band, a strap, a hat or any configuration thereof suitable to position screen shield or display 253 in front of a user's face.
- helmet 255 may include an augmented reality display incorporated by reference herein, U.S. Pat. No. 6,408,257 (“Harrington”).
- FIG. 5 a block diagram of architecture that is housed in PSER platform system 101 accordance with exemplary embodiments of the present disclosures illustrated.
- Exemplary embodiment includes software components, including base control system controller/processor 301 , input/output system 303 , data bus 305 , base control system recording medium/data storage device 307 , base control system motherboard/circuit board 313 , communication system 309 (including satellite or SATCOM) and optical communication systems (not shown) (e.g., UAV laser (see 181 B, FIGS. 3 and 181A , FIG. 10 )).
- base control system controller/processor 301 input/output system 303 , data bus 305 , base control system recording medium/data storage device 307 , base control system motherboard/circuit board 313 , communication system 309 (including satellite or SATCOM) and optical communication systems (not shown) (e.g., UAV laser (see 181 B, FIGS. 3 and 181A , FIG. 10 )).
- satellite or SATCOM
- BIT Test Built in Test system
- Computer system 133 monitors the optional battery pack 121 and load levels operation of UAV 107 , transmits telemetry data to mortar teams (e.g., see 401 , FIG. 7 ), controls and transmits fiber optic communications through fiber optic cable e.g., see 407 , FIG. 7 ) via tether 169 to UAV 107 , and controls the launch of UAV 107 .
- DPPPS 103 including guidance navigation system 323 , pulls on DPPPS cables (e.g., see 104 , FIG. 6 ) to control DPPPS 103 and guide PSER platform system (e.g., see 101 , FIG. 6 ) to target destination (e.g., see 381 , FIG. 6 ) via flight guidance control system 105 .
- DPPPS 103 is detached and optionally retrieve into parachute storage container 319 located in PSER platform system 101 . If target destination (e.g., see 381 , FIG. 6 ) is on water, expendable section 125 B (e.g., see FIG.
- Chute retrieval system 329 may be included in DPPPS 103 in some embodiments. Chute retrieval system 329 may be configured to pull detachable and reattachable cable (e see 131 , FIG. 6 ), coupled to DPPPS 103 , back into the PSER platform system 101 . Chute retrieval system 329 may be coupled to generator 119 or any other element that provides power to the base control system 300 and configured to pull via and suitable mechanical device, such as a winch, tension mechanism, crank, or other known device.
- Exemplary embodiment also includes generator 119 , fuel storage bladder 113 , fuel 114 , optional battery pack 121 , and power converter/electrical distribution 151 , which provides power to the base control system 300 , UAV 107 , and flight guidance control system 105 .
- auxiliary power source for example, solar panels may be disposed on PSER platform system 101 , to recharge optional battery pack 121 .
- Other embodiments may provide for fuel storage bladder 113 to include an opening such that it may be easily refueled (e.g., a mobile team refueling operation). In its non-deployed state, UAV 107 is coupled to UAV launch and recovery base system 325 .
- User control system 349 comprises a power system 351 , User control system controller/processor 353 , bus system 365 , and user control system data storage system 355 including software.
- Bus system 365 can be any suitable type of bus used in computing; whether parallel, bit series, or switched hubs connections and can include multidrop or daisy chain topology, or any other configuration known in the art.
- the user control system 349 can be connected via Input/output interfaces 357 .
- the Input/output interfaces 357 can also include, for example, a serial port, a parallel port, a small computer system interface (SCSI), an infrared (IR) interface, a radio frequency (RF) interface, a universal serial bus (USB) interface, and the like.
- the I/O interfaces 357 can include a user interface and graphical user interface (GUI) 367 that enables a user to interact with mobile devices. Additionally, the I/O interfaces 357 may further include an imaging device, i.e. camera, video camera, etc.
- the user control system 349 utilizes the User Interface and Graphical User Interface (GUI) System 367 including keyboard, display, etc. 359 , UAV maneuver and Equipment Control System (e.g., joystick and/or flight control system) 361 , and base control system communications system 363 to communicate with UAV 107 in flight or at UAV launch and recovery base system 325 when UAV 107 is grounded.
- GUI User Interface and Graphical User Interface
- PSER platform system is coupled to DPPPS 103 via detachable and reattachable cable 131 .
- DPPPS 103 After ejection from aircraft DPPPS 103 is deployed guiding PSER platform system 101 to target destination 381 .
- Propulsion system e.g., see 129 , FIG. 1
- guidance navigation system e.g., see 323 , FIG. 5
- Guidance navigation system controls DPPPS cables 104 , manipulating DPPPS 103 resulting in PSER platform system 101 being guided to target destination 381 .
- An operator e.g., mortar team 401 , FIG. 7
- PSER platform system's 101 guidance navigation system e.g., see 323 , FIG. 5
- satellite communications link such as with predator drones or localized control airship orbiting close by with high frequency (HF) remote control, to guide PSER platform system 101 to target destination 381 .
- HF high frequency
- an exemplary field of operation is shown with mortar team 401 using UAV 107 to accurately pinpoint the location of a target area 403 and accurately and reliably conveying information on the target area 403 to the mortar teams 401 in a field of combat.
- UAV 107 deploys from PSER platform system 101 , and conveys GPS data along with UAV camera (e.g., see 179 , FIG. 3 ) transmissions to mortar team 401 , where mortar team 401 monitors the target area 403 (e.g., monitoring enemy combatants) via exemplary soldier optics queuing system 251 .
- Mortar team 401 controls UAV's 107 movements and UAV camera (e.g., see 179 , FIG. 3 ) through use of user control system 349 .
- Communication link from the user control system 349 to the UAV's primary computer system e.g., see 189 , FIG. 3 ) can be wireless or wired.
- Tether 169 may carry a fiber optic cable 407 , ensuring no signal can be traced back to the location of PSER platform system 101 .
- communication may be transmitted wirelessly and power delivered to UAV 107 via auxiliary power source (e.g., see 173 , FIG. 3 ).
- laser light impulses from laser e.g., see 181 A, FIG. 10
- a photovoltaic power source e.g., see 172 , FIG. 3
- the location of and the subsequent movement of combatants within the target area 403 are captured by UAV camera (e.g., see 179 , FIG. 3 ) located on UAV 107 , and transmitted to mortar team 401 .
- Mortar team 401 can then quickly make correction in their next round of engagements on target.
- the system allows mortar team 401 to quickly eliminate or thwart unfriendly combatants within target area 403 and know whether to continue and assault or to evacuate the area to another firing location.
- Mortar teams 401 can also convey information about mortar success and combatant movement within target area 403 to allied infantry teams 405 who are closer to target area 403 .
- Laser pointer lines 409 are created by mortar teams 401 on the ground or by UAV 107 . These laser pointer lines 409 may be used in conjunction with UAV camera (e.g., see 179 , FIG. 3 ) to produce images such as FIGS. 8 and 9 .
- a GPS map 410 captured by camera (e.g., see 180 , FIG. 4 ) is shown allowing an operator (e.g., mortar team 401 , FIG. 7 ) to discern target areas.
- Laser pointer lines 409 are created by mortar team (e.g., see 401 , FIG. 7 ) on the ground or by UAV laser (e.g., see 181 B, FIG. 3 ) on UAV (e.g., see 107 , FIG. 3 ).
- Laser pointer lines 409 are created by laser (e.g., see laser 181 A, FIG. 10 ) or UAV laser (e.g., see 181 B, FIG. 3 ) is shown.
- laser pointer line 409 may be used in conjunction with camera (e.g., see 180 , FIG. 4 ) to produce images from FIGS. 8 and 9 .
- a functional diagram of the complementary components mounted on aircraft 502 is shown that includes an exemplary system can include a selective cable grapple system 507 comprising v-bars 515 and first selective or releasable cable grapple or coupling section (FRCGCS) 517 (e.g., shuttle track cargo rail/movement system), that is adapted to grapple a recovery cable 511 attached to a deployed recovery device 132 attaching the recovery cable 511 between the recovery device 132 and the PSER platform system 101 .
- FRCGCS 517 e.g., shuttle track cargo rail/movement system
- Some embodiments of the FRCGCS 517 comprise a track 518 that runs along a bottom of the aircraft 502 from front to back (e.g., edge of extendable rear cargo ramp).
- a grapple cable 520 may be disposed on the track 518 in such a manner that the grapple cable 520 may move freely along the length of the track 518 .
- a cable shuttle 522 may be attached to the grapple cable 520 so that it may move with the grapple cable 520 along the length of the track 518 .
- the cable shuttle 522 is configured to receive the recovery cable 511 after the recovery cable 511 has contacted the v-bars 515 . The cable shuttle 522 may then be configured to grasp a portion of the recovery cable 511 that is disposed in the cable shuttle 522 such that the portion of the recovery cable 511 moves with the cable shuttle 522 .
- the cable shuttle 522 may be configured to move towards the back of the aircraft 502 .
- the recovery device 132 can include a balloon, collapsible kite, parafoil system, or any device that upon deployment gains and/or maintains an altitude.
- the recovery device 132 is compactly stored on the PSER platform system 101 and when deployed extends the recovery cable 511 from a recovery cable spool 513 .
- the releasable couplers 126 may disengage when recovery device 132 is deployed allowing for retrievable section 125 A to move freely in relation to expendable section 125 B.
- the releasable couplers 126 may comprise any suitable configuration such that the couplers can be selectively detached, including, but not limited to adhesive, mechanical fasteners, fabric hook and look fasteners, electronically controlled latch, or any other method known in the art.
- the v-bars 515 can be a V or Y shaped system that guides the recovery cable 511 into the FRCGCS 517 .
- the v-bars may be positioned at the front of the aircraft 502 and configured to selectively cut the PSER platform system's 101 recovery device 132 loose so recovery device 132 flies up and over the aircraft 502 while FRCGCS 517 maintains coupling with the recovery cable 511 after it has been grappled/snagged by aircraft 502 .
- the PSER platform system 101 could be pulled underneath and behind the aircraft 502 .
- recovery cable 511 may be attached to retrievable section 125 A such that when the recovery cable is grappled/snagged by aircraft 502 , retrievable section 125 A is pulled up with the aircraft 502 , while expendable section 125 B remains on the ground/water.
- One variant can include an assembly where the recovery cable spool 513 can be the same device as (e.g., see 117 , FIG. 1 and e.g., see 153 , FIG. 2 ) that is coupled with the UAV (e.g., see 107 , FIG. 1 ). If the same device (e.g., see 117 , FIG. 1 and e.g., see 153 , FIG. 2 ) is used with the UAV (e.g., see 107 , FIG. 1 ) then a decoupler mechanism 525 (not shown) is provided in PSER platform system 101 that detaches tether (e.g., see 169 , FIG. 1 ) from the UAV (e.g., see 107 , FIG. 1 ) and couples it with the recovery device 132 .
- a decoupler mechanism 525 (not shown) is provided in PSER platform system 101 that detaches tether (e.g., see 169 , FIG. 1 ) from the
- a second selective or releasable cable grapple system (SRCGCS) 519 can be disposed or mounted in the aircraft 502 and may be configured so that the aircraft 502 , after flying and grappling recovery cable 511 and pulling the PSER platform system 101 off the ground, would grab or couple with the recovery cable 511 in proximity with the rear of the aircraft/ramp and reel the PSER platform system 101 into the aircraft 502 (e.g., C130 rear cargo hatch/ramp).
- SRCGCS selective or releasable cable grapple system
- the SRCGCS 519 may be coupled to the ramp and can comprise an extendable arm or crane 521 configured to reach out and snag the recovery cable 511 which is being dragged under the aircraft 502 in proximity to the ramp/hatch and then pull the recovery cable 511 and therefore the PSER platform system 101 up to and onto the aircraft 502 .
- Extendable arm or crane 521 may be manually operated by a user.
- a lock down/strap down system 526 can then be used to attach the recovered PSER platform system 101 to the aircraft 502 .
- the FRCGCS 517 may be configured to traverse backwards and pull the PSER platform system 101 towards the back of the aircraft 502 where the PSER platform system 101 is then lifted via SRCGCS 519 and moved into the airplane 502 .
- the PSER platform system 101 may be moved into the rear cargo hold of aircraft 502 .
- FRCGCS 517 can then be moved back into grappling position to grab a second PSER platform system (not shown).
- Embodiments can include a variant which has a shock absorbing system 529 is disposed on PSER platform system 101 .
- the shock absorbing system 529 may be included in the retrievable section 125 A, or in alternate embodiments, it may be included in expendable section 125 B, as shown in FIG. 11A .
- a variant can also have a partial release 550 (e.g., quick release) of elements of the PSER platform system 101 such as the optional battery pack (e.g., see 121 , FIG. 1 ), which lightens the overall PSER platform system's 101 weight and therefore reduces the load on the recovery cable 511 .
- a partial release 550 e.g., quick release
- elements of the PSER platform system 101 such as the optional battery pack (e.g., see 121 , FIG. 1 ), which lightens the overall PSER platform system's 101 weight and therefore reduces the load on the recovery cable 511 .
- An embodiment can include an inflatable or extendable/retracted aerodynamic shroud or fairing 552 (not shown) which creates a streamlined shape of the PSER platform system 101 , which can be deployed or extended when the recovery cable 511 is deployed via recovery device 132 .
- This inflatable or extendable/retracted aerodynamic shroud or fairing 552 can be coupled to the recovery cable 511 with lines 554 attached to the recovery cable 511 via a shroud or fairing deployment device 556 (e.g., a coupling ring) so that when the recovery device 132 deploys the recovery cable 511 passes through the shroud or fairing deployment device 556 until the recovery cable 511 is nearly fully extended and a stop 558 on the recovery cable 511 then pulls the shroud or fairing deployment device 556 up and extends the inflatable or extendable/retracted aerodynamic shroud or fairing 552 (not shown) around the PSER platform system 101 via the shroud or fairing deployment device 556 when the stop 558 on the recovery cable 511 extends to its fully extended position.
- the lines 554 can be routed so that they do not catch or tangle with other equipment on the PSER platform system 101 .
- Another variant can include a drag chute 562 (not shown) which is deployed after the PSER platform system 101 is airborne so that it applies a requisite degree of force on the PSER platform system 101 to bring it closer to the back end of the aircraft 502 so that the PSER platform system 101 is within selective cable grapple system's 507 range.
- a drag chute 562 (not shown) which is deployed after the PSER platform system 101 is airborne so that it applies a requisite degree of force on the PSER platform system 101 to bring it closer to the back end of the aircraft 502 so that the PSER platform system 101 is within selective cable grapple system's 507 range.
- the present disclosure provides a method of use of an exemplary UAV 107 with PSER platform system 101 .
- an operator completes a built-in test (“BIT Test”) using BIT Test check system 135 to test components including circuits, link, control servos, transmitter/receiver system and radiator/altimeter.
- Propulsion system 129 are energized via generator 119 and a satellite communications link is established.
- the PSER platform system 101 is deployed from an aircraft 502 at which time the DPPPS 103 guide PSER platform system 101 to land PSER platform system 101 at a target destination 381 with assistance of a propulsion system 129 , and a guidance navigation system 323 . If the PSER platform system 101 deviates from the target destination 381 an operator will take control via a satellite communications link with a high frequency remote control 383 and control the PSER platform system 101 to target destination 381 .
- the DPPPS 103 is detached from PSER platform system 101 .
- the UAV 107 , base control system 300 , and communications system 309 are activated.
- the UAV 107 is deployed from the PSER platform system 101 in either a tethered or untethered state.
- the UAV 107 is guided to a position vertically above the target area 403 .
- the UAV laser 181 B and UAV camera 179 on the UAV are used to spot the target area 403 using either wired or wireless communications to transmit information such as images, video, live video feed, light impulse signs, and communications to the mortar team 401 .
- step 801 H the UAV 107 is guided back into the PSER platform system 101 .
- the recovery device 132 is deployed extending a recovery cable 511 .
- the recovery cable 511 is selectively grappled to PSERFirst Selective or Releasable Cable Grapple or Coupling Section (FRCGCS) 517 on aircraft 502 .
- FRCGCS PSERFirst Selective or Releasable Cable Grapple or Coupling Section
- the PSER platform system 101 is then pulled underneath and behind and is reeled into aircraft 502 .
- the PSER platform system 101 is coupled, securing the PSER platform system 101 to the aircraft 502 .
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Radar, Positioning & Navigation (AREA)
- Signal Processing (AREA)
- Multimedia (AREA)
- Optics & Photonics (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
- Studio Devices (AREA)
Abstract
Description
- This application claims priority under 35 U.S.C. 119(e) of U.S. provisional patent application Ser. No. 62/561,563 filed on Sep. 21, 2017 entitled PERSISTENT SURVEILLANCE UNMANNED AERIAL VEHICLE AND LAUNCH/RECOVERY PLATFORM SYSTEM WITH SECURE COMMUNICATION, SENSOR SYSTEMS, TARGETING SYSTEMS, LOCATING SYSTEMS, AND PRECISION LANDING AND STABILIZATION SYSTEMS the disclosure of which is hereby incorporated herein by reference.
- The invention described herein was made in the performance of official duties by employees of the Department of the Navy and may be manufactured, used and licensed by or for the United States Government for any governmental purpose without payment of any royalties thereon. This invention (Navy Case 200,460) is assigned to the United States Government and is available for licensing for commercial purposes. Licensing and technical inquiries may be directed to the Technology Transfer Office, Naval Surface Warfare Center Crane, email: Cran_CTO@navy.mil.
- The field of the invention relates generally to unmanned airborne surveillance systems which provide persistent surveillance capabilities in austere or remote environments that lack access to a variety of resources (e.g., fuel resources) and are in a high risk environment thus require remote deployment and in some embodiments remote recovery. In particular, various embodiments of the invention include various self-contained elements along with sensor and communication capabilities including secure communication and visual sensors as well as remote targeting or geo-locating capabilities from a mobile platform with an air deployable power system.
- Existing systems do not meet various user requirements. Generally, a deployable or portable persistent surveillance requires rapid movement and setup; ability to operate in remote environments that is, in some cases, hostile or a denied movement environment; a robust, survivable, assured network communication capability, a networked enterprise to link and synchronize various tiers or systems of sensor system employment, data accessibility, and analytic effort; an enhanced system-level analytical and information exploitation tools that fill gaps in our ability to see and understand entities and activities within a given area or environment; planning tools and control methodologies for coordinating and controlling multiple data collection, analysis and information processing systems; and an ability to detect a change in the area or environment of interest. Surveillance paradigms are rapidly evolving from periodic, forensic surveillance to persistent surveillance reliant on integrated systems and predictive analysis. Based on the commander's prioritized requirements, persistent surveillance should capture both ongoing specific activity and, if necessary, forensically reconstruct activity after the event. Embodiments that are needed support a collection strategy that emphasizes an ability of some collections systems to linger on demand in an area to detect, locate, characterize, identify, track, target, and possibly provide battle damage assessment and re-targeting in real or near real time. Persistent surveillance facilitates the formulation and execution of preemptive activities to deter or forestall anticipated adversary courses of action. Various needs also include a capability supporting inclusion of synchronization and integration that reinforces operations and intelligence functions that are fully linked down to a lowest echelon and include sensors commonly associated with intelligence collection activities. Other capabilities that are needed include total sensor visibility, dynamic cueing, manned and unmanned teaming, and seamless system networking providing synchronization and integration elements. Additional capabilities include capacity to locate, track and target. Locate allows users to know precisely where the entity of interest is in an operational environment. Detection and location are not synonymous. Some sensors will only detect the entity then alert the system to focus its assets to precisely locate and characterize the entity. Tracking includes an ability to display or record the successive positions of a moving object in spite of natural obstacles or man-made countermeasures. This temporal requirement must be met to ensure that targets do not disappear and requires networked sensor integration and survivability. Targeting allows users to link all necessary entities or functions to address a given entity of interest or target as a mission requires which includes performance of a variety of tasks.
- Desired capabilities further include includes denial of sanctuary or ability to operate without being observed by providing persistent surveillance, tracking, and rapid engagement with high-volume precision task or application of effects. Another capability includes finding and performing tasks with respect to an entity while limiting unwanted effects such as collateral damage. Another set of desired capabilities includes developing a means to deny sanctuary to potential adversaries for a specific mission, area, and time period, support to application of long range systems to an entity of interest, extending surveillance and information collection across time, space, and information domains that is resistant to determined denial and deception efforts. Another desired need is to match a frequency of revisit with time stability of the object that a user is looking at—the speed with which things change. Another desired capability is support operations against any target, day or night, in any weather, and in denied or contested areas as well as enabling internetworking with other surveillance platforms or command nodes add gaining an understanding of entities of interest and operational environment continuously and in near real time to maneuver across strategic distances. Various limitations have been found in existing capabilities including: surveillance sensors are high demand/low density assets; users must prioritize and clearly define intelligence requirements and acknowledge risk in areas/objects not identified as priorities; achieved only for specific periods of time against extremely critical entities of interest; and dilutes efforts against other entities of interest priorities due to extended focus and allocation of sensors directed against one entity.
- In various embodiments it can be ideal to have a system that can accurately pinpoint the location of activity of interest and accurately and reliably convey information on location and activity to an exemplary user. At least some embodiments of the invention seeks to achieve real-time geo-location tracking of the activity via an aerial surveillance system that provides aerial surveillance capability to exemplary users such that they can know exactly where an activity of interest is located and provide real-time geo-location and positioning information for extremely accurate targeting of the activity of interest. Embodiments of this disclosure provides a user with precise targeting, without manned air assets, a base of operation that is highly mobile and allows swift relocation, and a capability to operate in a denied or hostile environment or in relatively close proximity to such an environment.
- An exemplary embodiment of the invention relates to an aerial surveillance system enabled by an aerial short wave infrared (SWIR) surveillance system platform for use in an exemplary field of operation where a quick response is preferred in reaction to real-time conditions by relaying the geo-location and other monitoring assistance via wireless or fiber SWIR optic links. An embodiment is capable of performance and deployment in many different conditions including any time of day (whether dark or light) and wide varieties of weather. Embodiments can include an aerial surveillance system that can be used in various applications such as to assist with base defenses, monitor parking lots or facilities, provide security monitoring, assist farmers planting fields, or assisting in the coordination of planting crops, or use by mortar crews in an exemplary hostile field of operation and in conjunction with mortars, e.g., the M30 mortar. According to a further illustrative embodiment of the present disclosure, an exemplary aerial surveillance system can be used to monitor any activity that would benefit from real-time information being relayed to the user.
- Additional features and advantages of the present invention will become apparent to those skilled in the art upon consideration of the following detailed description of the illustrative embodiment exemplifying the best mode of carrying out the invention as presently perceived.
- The detailed description of the drawings particularly refers to the accompanying figures in which:
-
FIG. 1 shows an exemplary longitudinal view (top) and partial cross section view (bottom) of an unmanned aerial vehicle (UAV) with launch, persistent surveillance enablement, and recovery (PSER) platform system in accordance with one exemplary embodiment; -
FIG. 2 shows an alternative exemplary longitudinal view and partial cross section of the exemplary UAV with PSER platform embodiments such as shown inFIG. 1 suitable for use with a tether power cable feed from a power transfer system, e.g., cone spool; -
FIG. 3 shows an exemplary longitudinal view and partial cross section of an UAV such as in, e.g.,FIG. 2 , utilized in an exemplary embodiment; -
FIG. 4 shows an exemplary user optics viewing or queuing system equipment of an exemplary embodiment that displays video and data outputs from the UAV; -
FIG. 5 shows a block diagram of an exemplary system architecture in accordance with exemplary embodiments of the present disclosure; -
FIG. 6 shows a longitudinal view of an airdrop system enabling autonomous navigation to a landing target for an exemplary PSER Platform System; -
FIG. 7 shows an exemplary embodiment in accordance with this disclosure of an aerial surveillance system in an exemplary operational context; -
FIG. 8 shows an aerial map view used in accordance with the exemplary surveillance system enabled by the present disclosure; -
FIG. 9 shows a screen shield view of a user video and data display system; -
FIG. 10 shows an example of laser spotting system used in relation one exemplary embodiment which would be viewable by optical systems on an exemplary UAV viewing an area which can be used as an aid in targeting; -
FIGS. 11A and 11B shows an exemplary base station/UAV recovery system and system architecture of an exemplary PSER platform in accordance with one exemplary embodiment; and -
FIGS. 12A and 12B shows a method of operating an exemplary embodiment of present disclosure. - Embodiments of the disclosure described herein are not intended to be exhaustive or to limit the disclosure to precise forms disclosed. Rather, the embodiments selected for description have been chosen to enable one skilled in the art to practice the disclosure.
- Referring initially to
FIG. 1 , a longitudinal and partial cross section view of anexemplary UAV 107 with an exemplaryPSER platform system 101 is shown. This exemplaryPSER platform system 101 includes afirst section 123 and asecond section 125. Thefirst section 123 andsecond section 125 are coupled to one another viaremovable coupling sections 120, e.g., cargo straps. Thefirst section 123 includes a deployable powered parachute or parafoil system (DPPPS) 103, a propulsion system 129 (optional), and a guidance navigation system (e.g., see 323, 5). The DPPPS 103 attaches to thefirst section 123 via a detachable andreattachable cable 131, which extends from theDPPPS 103 to thesecond section 125. An alternative embodiment can be provided that, upon landing, the DPPPS 103 retracts into a parachute storage container (e.g., see 319,FIG. 5 ). At the target destination (e.g., see 381,FIG. 6 ), acover 115 of thesecond section 125 retracts, allowing forUAV 107 to be deployed fromPSER platform system 101. Cover 115 may be retracted or opened through any suitable mechanical system, Thecover 115 can also be jettisoned as well including by, e.g., release mechanisms or servos (not shown) that are controlled by an onboard control system or if the cover retraction system malfunctions for example. - The
second section 125 ofPSER platform system 101 includes several components of the exemplary system comprising aUAV 107, UAV launch andrecovery base system 325,generator 119,tether 169,slip ring assembly 117, feedguide motor 111, fuel (e.g., see 114,FIG. 5 ), andfuel storage bladder 113. - The
second section 125 may include two separate subsections: aretrievable section 125A and anexpendable section 125B. In some embodiments,retrievable section 125A is releasably coupled toexpendable section 125B with releasable couplers 126 (two of which are shown butreleasable couplers 126 on opposing sides not shown). Thereleasable couplers 126 may be attached on each side of thesecond section 125. In other embodiments, there may be multiplereleasable couplers 126 on each side of thesecond section 125, while still other embodiments thereleasable couplers 126 may be attached on only one side ofsecond section 125 up to every side of thesecond section 125 or any arrangement in between to includereleasable couplers 126 between the two sections on an interior section or a non-side section. Within thesecond section 125, theUAV 107, in its non-deployable position, rests on UAV launch andrecovery base system 325, and may be selectively coupled togenerator 119 viatether 169. In some embodiments,UAV 107 may be disposed within theretrievable section 125A. Launch andrecovery base system 325 holds and locks intoplace UAV 107 when not in use. Launch and recovery base system may include a UAV retainer system (not shown) which is configured to hold the UAV in place while thePSER platform system 101 is in motion. In some embodiments, UAV retainer may include selectively coupling structures (e.g. servo operated clamps) that lock the UAV in place, while in other embodiments, other mechanical or electro-mechanical structures (e.g., Velcro® on the UAV landing structure and surface it rests upon) may be used to hold UAV in place to prevent damage whenPSER platform system 101 is in motion. Slack fromtether 169 may be coiled aroundslip ring assembly 117 untilUVA 107 deploys, at whichpoint tether 169 passes throughfeed guide motor 111 until fully extended.Feed guide motor 111 contains a reversing mechanism (e.g., see 112,FIG. 5 ) and reels tether 169 back ontoslip ring assembly 117 untilUAV 107 is coupled to launch andrecovery base system 325.Feed guide motor 111 also keeps tension ontether 169. Tether 169 connection increases flight time and prevents jamming and unfriendly or otherwise hostile control ofUAV 107. - In UAV's 107 deployed state,
UAV 107 may launch to about 3000 feet vertically, depending on the terrain. This exemplary launch height provides users with range and geo-location of enemy combatants within target area (e.g., see 403,FIG. 7 ) and prevents combatants from locatingPSER platform system 101. - Tether 169 also may transfer power from the
generator 119 to theUAV 107.Generator 119 is powered by fuel (e.g., see 114,FIG. 5 ) stored infuel storage bladder 113 or byoptional battery pack 121, both of which are stored in thesecond section 125. In some embodiments, thegenerator 119,fuel storage bladder 113 oroptional battery pack 121 may be included in theexpendable section 125B. Inother embodiments generator 119 may be disposed in theretrievable section 125A. TheUAV 107 may also deploy from thePSER platform system 101 in an untethered state and include its own auxiliary power source (e.g., see 173,FIG. 3 ). -
Expendable section 125B may by constructed to allow for safe landing at the target destination (e.g., see 381,FIG. 6 ). For example,expendable section 125B can optionally include a mechanism configured to safely disperse the force and lessen the impact of landing on hard surfaces, such as by using wooden boards, spring-like or shock absorber mechanisms, an adjustable pressure airbag, or a crush section (not shown) to absorb kinetic energy from a hard landing. - Alternatively,
expendable section 125B can optionally comprise a buoyancy system (e.g., see 321,FIG. 5 ) allowingPSER platform system 101 to float in water.PSER platform system 101 can then be optionally guided around the water with deployedUAV 107. An alternative embodiment may include an optional anchor system (e.g., see 327,FIG. 5 ), which anchorslaunch barrel 101 to the bottom of a body of water. This allows forPSER platform system 101 to remain in place ifUAV 107 is in its untethered state. Further alternative embodiments can also be provided with a drivetrain (not shown) and wheels (not shown) coupled with theexpendable section 125B and configured to be guided by personnel off-site via a remote connection. - The exemplary
PSER platform system 101 is adapted to be launched or ejected from an aircraft (e.g., see 502,FIG. 11B ), after which theDPPPS 103 deploys and expands guiding the exemplaryPSER platform system 101 to its target destination (e.g., see 381,FIG. 6 ). - Additionally, to conceal
PSER platform system 101, an optional PSER platformsystem concealment system 134 may cover at least a portion of thePSER platform system 101 resulting in thePSER platform system 101 being camouflaged with the surrounding environment. In one variant, PSERplatform concealment system 134 may be deployed upon landing such that a force against the bottom of thesecond section 125 will release the PSERplatform concealment system 134 to cloak or cover at least portions of thePSER platform system 101. Sections of the PSERplatform concealment system 134 can include camouflage, extendable sheets, etc. that can drop and unroll from a stored configuration via gravity and weights or extend from a roller controlled by a motor that roll down a guideline or track system at its edges, etc. These camouflage sections can be released from thesecond section 125 by servo controlled or mechanical latches connected to actuators of some type when thesecond section 125 is retrieved or extracted in order to lighten its weight. In some embodiments, thePSER platform system 101 may include a platform surveillance system (not shown). The surveillance system may comprise a camera to survey the environment and identify approaching threats. The camera may be configured to rotate 360 degrees around thePSER platform system 101. A motion detector may be included in the surveillance system and configured to activate the camera once movement is detected. The surveillance system can be in communication with the communications system (e.g., see 163,FIG. 3 ) or base control system 300 (shown inFIG. 5 ). For example, if surveillance system is activated, it can send a control signal or power command to a decoupler mechanism to detach theUAV 107 fromPSER platform system 101 so it will not be apprehended by hostiles. - Referring to
FIG. 2 , a longitudinal and partial cross-sectional view of an alternative embodiment of an exemplaryPSER platform system 101 is shown. In UAV's 107 non-deployed state, thetether 169 is coiled around afiber optic spool 153, replacing slip ring assembly (e.g., see 117,FIG. 1 ) and feed guide motor (e.g., see 111,FIG. 1 ), thereby reducing weight, as thefiber optic spool 153 weighs less than the slip ring assembly (e.g., see 117,FIG. 1 ) and feed guide motor (e.g., see 111,FIG. 1 ). Power converter/electrical distribution 151 within thesecond section 125 of thePSER platform system 101, which provides power to the base control system (e.g., see 300,FIG. 5 ),UAV 107, and UAV flight guidance control system (e.g., see 106,FIG. 3 ). In some embodiments,releasable couplers 126 may releasably coupleretrievable section 125A toexpendable section 125B. - Referring to
FIG. 3 , an exemplary longitudinal view and partial cross section ofUAV 107 utilized in an exemplary embodiment is shown.UAV 107 comprising anairframe 167, aUAV propulsion system 161, aprimary computer system 189, acommunications system 163, aUAV controller 165, aphotovoltaic power source 172,landing gear 177, asensor system 187, andoptional gripper 211. - In the preferred embodiment, the
UAV propulsion system 161 is associated withairframe 167 and comprisespropellers 171 coupled toelectric motors 175, providing the lift necessary for theUAV 107 to maintain flight. During flight one ormore landing gears 177 stabilize theUAV 107 and provide a structure for restingUAV 107 on a surface when not in flight.Propellers 171 may be about ten inches in length in this embodiment. Of course,propellers 171 may be longer or shorter than ten inches, depending on the implementation. TheUAV 107, includingelectric motors 175, are powered bytether 169 when in a tethered state. However,UAV 107, includingelectric motors 175, can be powered by UAVauxiliary power source 173. Theauxiliary power source 173 may be, for example, an electric battery, an engine that burns liquid fuel (e.g., internal combustion engine), or aphotovoltaic power source 172 powered by laser light impulses from a laser (e.g., see 181A,FIG. 10 ).Auxiliary power source 173 may also be swappable to enable persistent flight ofUAV 107. Whenauxiliary power source 173 is swappable, at least one other power source (e.g., tether 169) may be put in the place ofauxiliary power source 173 whileUAV 107 is using power. - The UAV
primary computer system 189 is associated with one ormore sensor systems 187 andcommunications systems 163 and comprisessoftware 260,non-volatile memory 262, input/output ports 264, acomputer system processor 213,GPS locator 212, and acontroller 165. -
Sensor system 187 is configured to generate information about the environment around and belowUAV 107.Sensor system 187 may comprise ofUAV camera 179,UAV laser 181B, and agimbal stabilizer 183 to stabilize sensors, which are configured to generate information about the environment aroundUAV 107 or generating information for mortar team (e.g., see 401,FIG. 7 ) such as laser pointer lines (e.g., see 409,FIG. 8 ).UAV camera 179 can be, for example, a still image camera, a video camera, an infrared camera, or a multispectral camera, configured to take and record images or videos, including live feed video, and transmit images or videos to the soldier optic queuing system (e.g., see 251,FIG. 4 ). In addition, thesensor system 187 may carry Light Detection and Ranging (LIDAR) 201,sonar 204, and traffic collision avoidance system (TCAS) 206. Data collected by thesensor system 187 may be stored on the device collecting the data (e.g., theUAV camera 179 if that camera captured that data), or the data may be stored onnon-volatile memory 262 of the UAVprimary computer system 189. - The
UAV 107 may use one ormore communications systems 163, such as a communication subsystem or wired subsystem, configured to provide communications betweenUAV 107 and another device via wireless or wired methods.Communications systems 163 may comprises radio transceivers 202, infrared devices 208, optical ultrasonic andelectromagnetic devices 210, andports 220 such asEthernet ports 220A, USB ports 220B,serial ports 220C, or other types of ports configured to establish a wired connection to theUAV 107 with other devices, such as a ground control station (GCS), flight planning system (FPS), or other devices, for example a mobile phone, tablet, personal computer, display monitor, other network-enabled devices.Communications system 163 can transmit a live video feeds to mortar teams (e.g., see 401,FIG. 7 ), signal them withUAV laser 181B in the field, as well as send SAT PHONE/COM info from radio transceivers 202. Additionally, thecommunications system 163 may optionally contain anRF signal source 185 emitted through thesensor system 187. One or more RF signals may be detectable by an payload, and or sensor systems. -
Controller 165 associated with UAVprimary computer system 189 may control operation of various systems within aUAV 107.Controller 165 may have aprocessor unit 230 and an autopilot feature 232 along with a desired level of intelligence to aid in the operation ofUAV 107.Controller 165 may receive commands, tasks, or other types of information depending on the level of intelligence ofcontroller 165. Further,controller 165 may operateUAV 107 using optional navigation software 234 in some embodiments. - Referring to
FIG. 4 , an isometric view of ahelmet 255 and a frontal view of a screen shield or display 253 of the soldieroptics queuing system 251, which comprises a screen shield ordisplay 253,helmet 255,camera 180,fan ventilator 267,battery pack 269, andUSB connection 271. Screen shield ordisplay 253 is coupled tohelmet 255 via attachment lugs 257. The screen shield or display 253 displays navigational 259,status 261, targeting 263, andtrajectory 265 data along with real-time images transmitted to screen shield or display 253 fromcamera 180. The screen shield or display can be a semi-transparent heads up display.Camera 180 can include thermal imaging camera, night vision, infrared, etc. In an alternative embodiment,camera 180 can be UAV camera (e.g., see 179,FIG. 3 ) located on UAV (e.g., see 107,FIG. 3 ). In other embodiments,helmet 255 can be replaced with any type of head mount that supports and orients solideroptics queuing system 251 or configured to fit on a user's head. The head mount may include an elastic band, a strap, a hat or any configuration thereof suitable to position screen shield ordisplay 253 in front of a user's face. In other embodiments,helmet 255 may include an augmented reality display incorporated by reference herein, U.S. Pat. No. 6,408,257 (“Harrington”). - Referring to
FIG. 5 , a block diagram of architecture that is housed inPSER platform system 101 accordance with exemplary embodiments of the present disclosures illustrated. Exemplary embodiment includes software components, including base control system controller/processor 301, input/output system 303, data bus 305, base control system recording medium/data storage device 307, base control system motherboard/circuit board 313, communication system 309 (including satellite or SATCOM) and optical communication systems (not shown) (e.g., UAV laser (see 181B,FIGS. 3 and 181A ,FIG. 10 )). Built in Test system (“BIT Test”) 135 is used to test and give integrity to computer system 133, including circuits, links, control servos, transmitter/receiver system and radiator/altimeter. Additionally,BIT Test 135 energizespropulsion system 129 via thegenerator 119 and establish satellite communications link. Computer system 133 (not shown) monitors theoptional battery pack 121 and load levels operation ofUAV 107, transmits telemetry data to mortar teams (e.g., see 401,FIG. 7 ), controls and transmits fiber optic communications through fiber optic cable e.g., see 407,FIG. 7 ) viatether 169 toUAV 107, and controls the launch ofUAV 107. -
DPPPS 103, includingguidance navigation system 323, pulls on DPPPS cables (e.g., see 104,FIG. 6 ) to controlDPPPS 103 and guide PSER platform system (e.g., see 101,FIG. 6 ) to target destination (e.g., see 381,FIG. 6 ) via flightguidance control system 105. At target destination (e.g., see 381,FIG. 6 ),DPPPS 103 is detached and optionally retrieve into parachute storage container 319 located inPSER platform system 101. If target destination (e.g., see 381,FIG. 6 ) is on water,expendable section 125B (e.g., seeFIG. 1 ) may include a buoyancy system 321 allowingPSER platform system 101 to float in water, and be guided around the water via theUAV 107. An alternative embodiment may include an optional anchor system 327 which anchorsPSER platform system 101 to the bottom of a body of water.Chute retrieval system 329 may be included inDPPPS 103 in some embodiments.Chute retrieval system 329 may be configured to pull detachable and reattachable cable (e see 131,FIG. 6 ), coupled toDPPPS 103, back into thePSER platform system 101.Chute retrieval system 329 may be coupled togenerator 119 or any other element that provides power to thebase control system 300 and configured to pull via and suitable mechanical device, such as a winch, tension mechanism, crank, or other known device. - Exemplary embodiment also includes
generator 119,fuel storage bladder 113, fuel 114,optional battery pack 121, and power converter/electrical distribution 151, which provides power to thebase control system 300,UAV 107, and flightguidance control system 105. In some embodiments, auxiliary power source, for example, solar panels may be disposed onPSER platform system 101, to rechargeoptional battery pack 121. Other embodiments may provide forfuel storage bladder 113 to include an opening such that it may be easily refueled (e.g., a mobile team refueling operation). In its non-deployed state,UAV 107 is coupled to UAV launch andrecovery base system 325. - Further referring to
FIG. 5 , a block diagram of the software architecture in accordance with theuser control system 349 in which the present disclosure can be implemented.User control system 349 comprises a power system 351, User control system controller/processor 353, bus system 365, and user control system data storage system 355 including software. Bus system 365 can be any suitable type of bus used in computing; whether parallel, bit series, or switched hubs connections and can include multidrop or daisy chain topology, or any other configuration known in the art. Theuser control system 349 can be connected via Input/output interfaces 357. The Input/output interfaces 357 can also include, for example, a serial port, a parallel port, a small computer system interface (SCSI), an infrared (IR) interface, a radio frequency (RF) interface, a universal serial bus (USB) interface, and the like. The I/O interfaces 357 can include a user interface and graphical user interface (GUI) 367 that enables a user to interact with mobile devices. Additionally, the I/O interfaces 357 may further include an imaging device, i.e. camera, video camera, etc. - The
user control system 349 utilizes the User Interface and Graphical User Interface (GUI) System 367 including keyboard, display, etc. 359, UAV maneuver and Equipment Control System (e.g., joystick and/or flight control system) 361, and base control system communications system 363 to communicate withUAV 107 in flight or at UAV launch andrecovery base system 325 whenUAV 107 is grounded. - Referring to
FIG. 6 , navigation ofPSER platform system 101 to targetdestination 381 is depicted. PSER platform system is coupled to DPPPS 103 via detachable andreattachable cable 131. After ejection fromaircraft DPPPS 103 is deployed guidingPSER platform system 101 to targetdestination 381. Propulsion system (e.g., see 129,FIG. 1 ) and guidance navigation system (e.g., see 323,FIG. 5 ) aid in directingPSER platform system 101 to targetdestination 381. Guidance navigation system (e.g., see 323,FIG. 5 ) controlsDPPPS cables 104, manipulatingDPPPS 103 resulting inPSER platform system 101 being guided to targetdestination 381. An operator (e.g.,mortar team 401,FIG. 7 ) can optionally take control of PSER platform system's 101 guidance navigation system (e.g., see 323,FIG. 5 ) via satellite communications link, such as with predator drones or localized control airship orbiting close by with high frequency (HF) remote control, to guidePSER platform system 101 to targetdestination 381. - Referring to
FIG. 7 , an exemplary field of operation is shown withmortar team 401 usingUAV 107 to accurately pinpoint the location of atarget area 403 and accurately and reliably conveying information on thetarget area 403 to themortar teams 401 in a field of combat. - Here,
UAV 107 deploys fromPSER platform system 101, and conveys GPS data along with UAV camera (e.g., see 179,FIG. 3 ) transmissions tomortar team 401, wheremortar team 401 monitors the target area 403 (e.g., monitoring enemy combatants) via exemplary soldieroptics queuing system 251.Mortar team 401 controls UAV's 107 movements and UAV camera (e.g., see 179,FIG. 3 ) through use ofuser control system 349. Communication link from theuser control system 349 to the UAV's primary computer system (e.g., see 189,FIG. 3 ) can be wireless or wired. When deploying theUAV 107 in the tethered state, communications and power is transmitted toUAV 107 viatether 169. Tether 169 may carry afiber optic cable 407, ensuring no signal can be traced back to the location ofPSER platform system 101. Additionally, in UAV's 107 untethered state, communication may be transmitted wirelessly and power delivered toUAV 107 via auxiliary power source (e.g., see 173,FIG. 3 ). In an alternative embodiment, laser light impulses from laser (e.g., see 181A,FIG. 10 ) interact with a photovoltaic power source (e.g., see 172,FIG. 3 ) topower UAV 107 and keeptether 169 from overheating. - The location of and the subsequent movement of combatants within the
target area 403 are captured by UAV camera (e.g., see 179,FIG. 3 ) located onUAV 107, and transmitted tomortar team 401.Mortar team 401 can then quickly make correction in their next round of engagements on target. The system allowsmortar team 401 to quickly eliminate or thwart unfriendly combatants withintarget area 403 and know whether to continue and assault or to evacuate the area to another firing location.Mortar teams 401 can also convey information about mortar success and combatant movement withintarget area 403 toallied infantry teams 405 who are closer to targetarea 403.Laser pointer lines 409 are created bymortar teams 401 on the ground or byUAV 107. Theselaser pointer lines 409 may be used in conjunction with UAV camera (e.g., see 179,FIG. 3 ) to produce images such asFIGS. 8 and 9 . - Referring to
FIG. 8 , aGPS map 410 captured by camera (e.g., see 180,FIG. 4 ) is shown allowing an operator (e.g.,mortar team 401,FIG. 7 ) to discern target areas.Laser pointer lines 409 are created by mortar team (e.g., see 401,FIG. 7 ) on the ground or by UAV laser (e.g., see 181B,FIG. 3 ) on UAV (e.g., see 107,FIG. 3 ). - Referring to
FIG. 9 , an example of a screen shield or display 253 view is depicted.Laser pointer lines 409 are created by laser (e.g., seelaser 181A,FIG. 10 ) or UAV laser (e.g., see 181B,FIG. 3 ) is shown. - Referring to
FIG. 10 , exemplary use oflaser 181A bymortar team 401 is shown. Whenmortar team 401 operateslaser 181A,laser pointer line 409 are created.Laser pointer line 409 may be used in conjunction with camera (e.g., see 180,FIG. 4 ) to produce images fromFIGS. 8 and 9 . - Referring to
FIG. 11A andFIG. 11B , a functional diagram of the complementary components mounted onaircraft 502 is shown that includes an exemplary system can include a selective cable grapplesystem 507 comprising v-bars 515 and first selective or releasable cable grapple or coupling section (FRCGCS) 517 (e.g., shuttle track cargo rail/movement system), that is adapted to grapple arecovery cable 511 attached to a deployedrecovery device 132 attaching therecovery cable 511 between therecovery device 132 and thePSER platform system 101. Some embodiments of theFRCGCS 517 comprise atrack 518 that runs along a bottom of theaircraft 502 from front to back (e.g., edge of extendable rear cargo ramp). A grapplecable 520 may be disposed on thetrack 518 in such a manner that the grapplecable 520 may move freely along the length of thetrack 518. Acable shuttle 522 may be attached to the grapplecable 520 so that it may move with the grapplecable 520 along the length of thetrack 518. In some embodiments, thecable shuttle 522 is configured to receive therecovery cable 511 after therecovery cable 511 has contacted the v-bars 515. Thecable shuttle 522 may then be configured to grasp a portion of therecovery cable 511 that is disposed in thecable shuttle 522 such that the portion of therecovery cable 511 moves with thecable shuttle 522. After grasping therecovery cable 511, thecable shuttle 522 may be configured to move towards the back of theaircraft 502. Therecovery device 132 can include a balloon, collapsible kite, parafoil system, or any device that upon deployment gains and/or maintains an altitude. Therecovery device 132 is compactly stored on thePSER platform system 101 and when deployed extends therecovery cable 511 from arecovery cable spool 513. Thereleasable couplers 126 may disengage whenrecovery device 132 is deployed allowing forretrievable section 125A to move freely in relation toexpendable section 125B. Thereleasable couplers 126 may comprise any suitable configuration such that the couplers can be selectively detached, including, but not limited to adhesive, mechanical fasteners, fabric hook and look fasteners, electronically controlled latch, or any other method known in the art. - The v-
bars 515 can be a V or Y shaped system that guides therecovery cable 511 into theFRCGCS 517. The v-bars may be positioned at the front of theaircraft 502 and configured to selectively cut the PSER platform system's 101recovery device 132 loose sorecovery device 132 flies up and over theaircraft 502 whileFRCGCS 517 maintains coupling with therecovery cable 511 after it has been grappled/snagged byaircraft 502. ThePSER platform system 101 could be pulled underneath and behind theaircraft 502. In some embodiments,recovery cable 511 may be attached toretrievable section 125A such that when the recovery cable is grappled/snagged byaircraft 502,retrievable section 125A is pulled up with theaircraft 502, whileexpendable section 125B remains on the ground/water. - One variant can include an assembly where the
recovery cable spool 513 can be the same device as (e.g., see 117,FIG. 1 and e.g., see 153,FIG. 2 ) that is coupled with the UAV (e.g., see 107,FIG. 1 ). If the same device (e.g., see 117,FIG. 1 and e.g., see 153,FIG. 2 ) is used with the UAV (e.g., see 107,FIG. 1 ) then a decoupler mechanism 525 (not shown) is provided inPSER platform system 101 that detaches tether (e.g., see 169,FIG. 1 ) from the UAV (e.g., see 107,FIG. 1 ) and couples it with therecovery device 132. - A second selective or releasable cable grapple system (SRCGCS) 519 can be disposed or mounted in the
aircraft 502 and may be configured so that theaircraft 502, after flying and grapplingrecovery cable 511 and pulling thePSER platform system 101 off the ground, would grab or couple with therecovery cable 511 in proximity with the rear of the aircraft/ramp and reel thePSER platform system 101 into the aircraft 502 (e.g., C130 rear cargo hatch/ramp). In some embodiments, theSRCGCS 519 may be coupled to the ramp and can comprise an extendable arm orcrane 521 configured to reach out and snag therecovery cable 511 which is being dragged under theaircraft 502 in proximity to the ramp/hatch and then pull therecovery cable 511 and therefore thePSER platform system 101 up to and onto theaircraft 502. Extendable arm orcrane 521 may be manually operated by a user. A lock down/strap downsystem 526 can then be used to attach the recoveredPSER platform system 101 to theaircraft 502. - In some embodiments the
FRCGCS 517 may be configured to traverse backwards and pull thePSER platform system 101 towards the back of theaircraft 502 where thePSER platform system 101 is then lifted viaSRCGCS 519 and moved into theairplane 502. For example, thePSER platform system 101 may be moved into the rear cargo hold ofaircraft 502.FRCGCS 517 can then be moved back into grappling position to grab a second PSER platform system (not shown). - Embodiments can include a variant which has a shock absorbing system 529 is disposed on
PSER platform system 101. The shock absorbing system 529 may be included in theretrievable section 125A, or in alternate embodiments, it may be included inexpendable section 125B, as shown inFIG. 11A . - A variant can also have a partial release 550 (e.g., quick release) of elements of the
PSER platform system 101 such as the optional battery pack (e.g., see 121,FIG. 1 ), which lightens the overall PSER platform system's 101 weight and therefore reduces the load on therecovery cable 511. - An embodiment can include an inflatable or extendable/retracted aerodynamic shroud or fairing 552 (not shown) which creates a streamlined shape of the
PSER platform system 101, which can be deployed or extended when therecovery cable 511 is deployed viarecovery device 132. This inflatable or extendable/retracted aerodynamic shroud or fairing 552 can be coupled to therecovery cable 511 withlines 554 attached to therecovery cable 511 via a shroud or fairing deployment device 556 (e.g., a coupling ring) so that when therecovery device 132 deploys therecovery cable 511 passes through the shroud or fairing deployment device 556 until therecovery cable 511 is nearly fully extended and astop 558 on therecovery cable 511 then pulls the shroud or fairing deployment device 556 up and extends the inflatable or extendable/retracted aerodynamic shroud or fairing 552 (not shown) around thePSER platform system 101 via the shroud or fairing deployment device 556 when thestop 558 on therecovery cable 511 extends to its fully extended position. Thelines 554 can be routed so that they do not catch or tangle with other equipment on thePSER platform system 101. - Another variant can include a drag chute 562 (not shown) which is deployed after the
PSER platform system 101 is airborne so that it applies a requisite degree of force on thePSER platform system 101 to bring it closer to the back end of theaircraft 502 so that thePSER platform system 101 is within selective cable grapple system's 507 range. - Referring to
FIG. 12A , the present disclosure provides a method of use of anexemplary UAV 107 withPSER platform system 101. At step 801A, an operator completes a built-in test (“BIT Test”) using BITTest check system 135 to test components including circuits, link, control servos, transmitter/receiver system and radiator/altimeter.Propulsion system 129 are energized viagenerator 119 and a satellite communications link is established. - At step 801B, the
PSER platform system 101 is deployed from anaircraft 502 at which time theDPPPS 103 guidePSER platform system 101 to landPSER platform system 101 at atarget destination 381 with assistance of apropulsion system 129, and aguidance navigation system 323. If thePSER platform system 101 deviates from thetarget destination 381 an operator will take control via a satellite communications link with a high frequency remote control 383 and control thePSER platform system 101 to targetdestination 381. - At
step 801C theDPPPS 103 is detached fromPSER platform system 101. Atstep 801D theUAV 107,base control system 300, andcommunications system 309 are activated. Atstep 801E, theUAV 107 is deployed from thePSER platform system 101 in either a tethered or untethered state. Atstep 801F, theUAV 107 is guided to a position vertically above thetarget area 403. At step 801G, theUAV laser 181B andUAV camera 179 on the UAV are used to spot thetarget area 403 using either wired or wireless communications to transmit information such as images, video, live video feed, light impulse signs, and communications to themortar team 401. - At
step 801H, theUAV 107 is guided back into thePSER platform system 101. - Referring to
FIG. 12B , at step 801I, therecovery device 132 is deployed extending arecovery cable 511. At step, 801J, therecovery cable 511 is selectively grappled to PSERFirst Selective or Releasable Cable Grapple or Coupling Section (FRCGCS) 517 onaircraft 502. Atstep 801K, thePSER platform system 101 is then pulled underneath and behind and is reeled intoaircraft 502. Atstep 801L, thePSER platform system 101 is coupled, securing thePSER platform system 101 to theaircraft 502. - Although the disclosure has been described in detail with reference to certain preferred embodiments, variations and modifications exist within the spirit and scope of the disclosures described and defined in the following claims.
Claims (28)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/885,152 US10890927B2 (en) | 2017-09-21 | 2018-01-31 | Persistent surveillance unmanned aerial vehicle and launch/recovery platform system and method of using with secure communication, sensor systems, targeting systems, locating systems, and precision landing and stabilization systems |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201762561563P | 2017-09-21 | 2017-09-21 | |
US15/885,152 US10890927B2 (en) | 2017-09-21 | 2018-01-31 | Persistent surveillance unmanned aerial vehicle and launch/recovery platform system and method of using with secure communication, sensor systems, targeting systems, locating systems, and precision landing and stabilization systems |
Publications (2)
Publication Number | Publication Date |
---|---|
US20190086920A1 true US20190086920A1 (en) | 2019-03-21 |
US10890927B2 US10890927B2 (en) | 2021-01-12 |
Family
ID=65720330
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/885,152 Active 2038-10-09 US10890927B2 (en) | 2017-09-21 | 2018-01-31 | Persistent surveillance unmanned aerial vehicle and launch/recovery platform system and method of using with secure communication, sensor systems, targeting systems, locating systems, and precision landing and stabilization systems |
Country Status (1)
Country | Link |
---|---|
US (1) | US10890927B2 (en) |
Cited By (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170161961A1 (en) * | 2015-12-07 | 2017-06-08 | Paul Salsberg | Parking space control method and system with unmanned paired aerial vehicle (uav) |
CN110329530A (en) * | 2019-07-22 | 2019-10-15 | 黑龙江大学 | A kind of aerial low-speed unmanned aerial vehicle recyclable device of ejection net catching type |
CN110341966A (en) * | 2019-08-20 | 2019-10-18 | 纪衍雨 | A kind of multi-functional full-automatic parachute |
US20190335131A1 (en) * | 2018-04-27 | 2019-10-31 | Vital Optics, Inc | Monitoring System with Heads-Up Display |
CN110498064A (en) * | 2019-09-12 | 2019-11-26 | 中国人民解放军战略支援部队航天工程大学 | A kind of fairing of launch vehicle recovery scheme |
CN110525677A (en) * | 2019-08-21 | 2019-12-03 | 侯百文 | A kind of liquid cooling power transmission is electronic to be tethered at UAV system |
CN111017246A (en) * | 2019-11-21 | 2020-04-17 | 东南大学 | Airborne multi-motor series power supply circuit of tethered unmanned aerial vehicle |
CN111726571A (en) * | 2020-01-05 | 2020-09-29 | 杨文娟 | High-voltage line distribution shape detection system |
CN112046751A (en) * | 2020-08-31 | 2020-12-08 | 南京理工大学 | Test bullet drop platform based on many rotor unmanned aerial vehicle |
US10864996B1 (en) * | 2020-02-21 | 2020-12-15 | Husam J. Abdalwahid | Apparatus and method of monitoring and securing aircraft |
US20210061466A1 (en) * | 2019-09-03 | 2021-03-04 | Howard Gee | Monitoring events employing a drone having a camera controlled via an application |
US11079568B2 (en) * | 2017-11-20 | 2021-08-03 | Airbus Defence And Space Sas | Payload module for stratospheric drone |
US20210237839A1 (en) * | 2018-05-02 | 2021-08-05 | Modern Technology Solutions, Inc. | Rapid aerial extraction systems |
US20210253241A1 (en) * | 2020-02-19 | 2021-08-19 | Gad HARAN | Electric vehicle with an airborne link device for connecting to a power line and an airborne link device thereof |
US11124298B2 (en) * | 2016-05-28 | 2021-09-21 | SZ DJI Technology Co., Ltd. | Foldable UAV |
WO2022010511A1 (en) * | 2020-07-09 | 2022-01-13 | Smartdrone Corporation | Sensor mounting system |
US11449054B2 (en) * | 2019-08-26 | 2022-09-20 | Lg Electronics Inc. | Method for controlling flight of unmanned aerial robot by unmanned aerial system and apparatus supporting the same |
CN115123494A (en) * | 2022-08-15 | 2022-09-30 | 威海海洋职业学院 | Unmanned aerial vehicle device for assisting marine life-saving |
CN116719091A (en) * | 2023-06-08 | 2023-09-08 | 中国矿业大学 | Natural potential detection system based on tethered unmanned aerial vehicle |
US20230314141A1 (en) * | 2020-01-21 | 2023-10-05 | The Boeing Company | Terrain referenced navigation system with generic terrain sensors for correcting an inertial navigation solution |
CN117584155A (en) * | 2024-01-18 | 2024-02-23 | 内蒙古工业大学 | Intelligent carrying mechanism of wall-climbing type photovoltaic cleaning robot |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11086025B2 (en) * | 2015-08-13 | 2021-08-10 | Propeller Aerobotics Pty Ltd | Integrated visual geo-referencing target unit and method of operation |
US11498701B2 (en) * | 2020-04-06 | 2022-11-15 | Workhorse Group Inc. | Flying vehicle systems and methods |
US20230271731A1 (en) * | 2022-01-11 | 2023-08-31 | Government Of The United States, As Represented By The Secretary Of The Air Force | Plural relay sensor method of delivery |
Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100034424A1 (en) * | 2008-08-06 | 2010-02-11 | Honeywell International Inc. | Pointing system for laser designator |
US20120044710A1 (en) * | 2010-08-17 | 2012-02-23 | Jones Kenneth R | Aerially Deployed Illumination System |
US20130233964A1 (en) * | 2012-03-07 | 2013-09-12 | Aurora Flight Sciences Corporation | Tethered aerial system for data gathering |
US20140263852A1 (en) * | 2013-03-15 | 2014-09-18 | CyPhy Works, Inc. | Spooler for unmanned aerial vehicle system |
US20160138893A1 (en) * | 2010-03-22 | 2016-05-19 | Omnitek Partners Llc | Remotely guided gun-fired and mortar rounds |
US20180009549A1 (en) * | 2016-07-05 | 2018-01-11 | Toyota Motor Engineering & Manufacturing North America, Inc. | Systems for transporting, deploying, and docking unmanned aerial vehicles mountable on a ground vehicle |
US20180059660A1 (en) * | 2016-08-23 | 2018-03-01 | Group Care Technologies, LLC | Intelligent event response with unmanned aerial system |
US20180118374A1 (en) * | 2016-07-29 | 2018-05-03 | Stabilis Inc. | Ground station and tether for unmanned aerial vehicles |
US20180255465A1 (en) * | 2015-04-14 | 2018-09-06 | ETAK Systems, LLC | Systems and methods for delivering a close out package for work done at a telecommunications site |
US20190068953A1 (en) * | 2017-08-25 | 2019-02-28 | Aurora Flight Sciences Corporation | Aerial Vehicle Imaging and Targeting System |
-
2018
- 2018-01-31 US US15/885,152 patent/US10890927B2/en active Active
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20100034424A1 (en) * | 2008-08-06 | 2010-02-11 | Honeywell International Inc. | Pointing system for laser designator |
US20160138893A1 (en) * | 2010-03-22 | 2016-05-19 | Omnitek Partners Llc | Remotely guided gun-fired and mortar rounds |
US20120044710A1 (en) * | 2010-08-17 | 2012-02-23 | Jones Kenneth R | Aerially Deployed Illumination System |
US20130233964A1 (en) * | 2012-03-07 | 2013-09-12 | Aurora Flight Sciences Corporation | Tethered aerial system for data gathering |
US20140263852A1 (en) * | 2013-03-15 | 2014-09-18 | CyPhy Works, Inc. | Spooler for unmanned aerial vehicle system |
US20180255465A1 (en) * | 2015-04-14 | 2018-09-06 | ETAK Systems, LLC | Systems and methods for delivering a close out package for work done at a telecommunications site |
US20180009549A1 (en) * | 2016-07-05 | 2018-01-11 | Toyota Motor Engineering & Manufacturing North America, Inc. | Systems for transporting, deploying, and docking unmanned aerial vehicles mountable on a ground vehicle |
US20180118374A1 (en) * | 2016-07-29 | 2018-05-03 | Stabilis Inc. | Ground station and tether for unmanned aerial vehicles |
US20180059660A1 (en) * | 2016-08-23 | 2018-03-01 | Group Care Technologies, LLC | Intelligent event response with unmanned aerial system |
US20190068953A1 (en) * | 2017-08-25 | 2019-02-28 | Aurora Flight Sciences Corporation | Aerial Vehicle Imaging and Targeting System |
Cited By (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170161961A1 (en) * | 2015-12-07 | 2017-06-08 | Paul Salsberg | Parking space control method and system with unmanned paired aerial vehicle (uav) |
US11124298B2 (en) * | 2016-05-28 | 2021-09-21 | SZ DJI Technology Co., Ltd. | Foldable UAV |
US11079568B2 (en) * | 2017-11-20 | 2021-08-03 | Airbus Defence And Space Sas | Payload module for stratospheric drone |
US20190335131A1 (en) * | 2018-04-27 | 2019-10-31 | Vital Optics, Inc | Monitoring System with Heads-Up Display |
US10771727B2 (en) * | 2018-04-27 | 2020-09-08 | Vital Optics, Inc | Monitoring system with heads-up display |
US12065225B2 (en) * | 2018-05-02 | 2024-08-20 | Modern Technology Solutions, Inc. | Rapid aerial extraction systems |
US12012188B2 (en) * | 2018-05-02 | 2024-06-18 | Modern Technology Solutions, Inc. | Rapid aerial extraction systems |
US20240010311A1 (en) * | 2018-05-02 | 2024-01-11 | Modern Technology Solutions, Inc. | Rapid aerial extraction systems |
US20210237839A1 (en) * | 2018-05-02 | 2021-08-05 | Modern Technology Solutions, Inc. | Rapid aerial extraction systems |
CN110329530A (en) * | 2019-07-22 | 2019-10-15 | 黑龙江大学 | A kind of aerial low-speed unmanned aerial vehicle recyclable device of ejection net catching type |
CN110341966A (en) * | 2019-08-20 | 2019-10-18 | 纪衍雨 | A kind of multi-functional full-automatic parachute |
CN110525677A (en) * | 2019-08-21 | 2019-12-03 | 侯百文 | A kind of liquid cooling power transmission is electronic to be tethered at UAV system |
US11449054B2 (en) * | 2019-08-26 | 2022-09-20 | Lg Electronics Inc. | Method for controlling flight of unmanned aerial robot by unmanned aerial system and apparatus supporting the same |
US20210061466A1 (en) * | 2019-09-03 | 2021-03-04 | Howard Gee | Monitoring events employing a drone having a camera controlled via an application |
CN110498064A (en) * | 2019-09-12 | 2019-11-26 | 中国人民解放军战略支援部队航天工程大学 | A kind of fairing of launch vehicle recovery scheme |
CN111017246A (en) * | 2019-11-21 | 2020-04-17 | 东南大学 | Airborne multi-motor series power supply circuit of tethered unmanned aerial vehicle |
CN111726571A (en) * | 2020-01-05 | 2020-09-29 | 杨文娟 | High-voltage line distribution shape detection system |
US20230314141A1 (en) * | 2020-01-21 | 2023-10-05 | The Boeing Company | Terrain referenced navigation system with generic terrain sensors for correcting an inertial navigation solution |
US11821733B2 (en) * | 2020-01-21 | 2023-11-21 | The Boeing Company | Terrain referenced navigation system with generic terrain sensors for correcting an inertial navigation solution |
US20210253241A1 (en) * | 2020-02-19 | 2021-08-19 | Gad HARAN | Electric vehicle with an airborne link device for connecting to a power line and an airborne link device thereof |
US10864996B1 (en) * | 2020-02-21 | 2020-12-15 | Husam J. Abdalwahid | Apparatus and method of monitoring and securing aircraft |
WO2022010511A1 (en) * | 2020-07-09 | 2022-01-13 | Smartdrone Corporation | Sensor mounting system |
CN112046751A (en) * | 2020-08-31 | 2020-12-08 | 南京理工大学 | Test bullet drop platform based on many rotor unmanned aerial vehicle |
CN115123494A (en) * | 2022-08-15 | 2022-09-30 | 威海海洋职业学院 | Unmanned aerial vehicle device for assisting marine life-saving |
CN116719091A (en) * | 2023-06-08 | 2023-09-08 | 中国矿业大学 | Natural potential detection system based on tethered unmanned aerial vehicle |
CN117584155A (en) * | 2024-01-18 | 2024-02-23 | 内蒙古工业大学 | Intelligent carrying mechanism of wall-climbing type photovoltaic cleaning robot |
Also Published As
Publication number | Publication date |
---|---|
US10890927B2 (en) | 2021-01-12 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US10890927B2 (en) | Persistent surveillance unmanned aerial vehicle and launch/recovery platform system and method of using with secure communication, sensor systems, targeting systems, locating systems, and precision landing and stabilization systems | |
JP7185033B2 (en) | Close Proximity Countermeasures for Neutralization of Target Aircraft | |
US11373539B2 (en) | Unmanned aerial vehicle management | |
US10800546B2 (en) | Unmanned aerial vehicle (UAV) and system and method for capture of threat UAVs | |
US5927648A (en) | Aircraft based sensing, detection, targeting, communications and response apparatus | |
US9688401B2 (en) | Methods and systems for retrieving personnel | |
US10399674B2 (en) | Systems and methods countering an unmanned air vehicle | |
US8973860B2 (en) | Aerial recovery of small and micro air vehicles | |
EP2490940B1 (en) | Uav system and method | |
US11396375B2 (en) | Modular unmanned aerial system | |
KR20210066874A (en) | Countermeasure deployment system to facilitate neutralization of target air vehicles | |
US5906336A (en) | Method and apparatus for temporarily interconnecting an unmanned aerial vehicle | |
US8038090B2 (en) | System and method for the retrieval of a smaller unmanned aerial vehicle by a larger unmanned aerial vehicle | |
CN107655362A (en) | Multimode unmanned aerial vehicle | |
US7053812B2 (en) | Recoverable pod for self-protection of aircraft and method of protecting an aircraft using a recoverable pod | |
US20180251218A1 (en) | Space Combat Drone | |
US20180037321A1 (en) | Law enforcement drone | |
US9716862B1 (en) | System and methods for capturing situational awareness | |
Barazzotto | Thoughts on betting your beast of burden and winning: part II | |
Wood | Drone Operator | |
JOGERST | Airpower Trends 2010 | |
Dorn | Aerial Surveillance: Eyes in the Sky: Why Students Fail | |
Kovács | PAYLOAD OF UNMANNED AERIAL VEHICLES. | |
SREY | L POSTGI'SREY, C |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
FEPP | Fee payment procedure |
Free format text: ENTITY STATUS SET TO UNDISCOUNTED (ORIGINAL EVENT CODE: BIG.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
AS | Assignment |
Owner name: UNITED STATES OF AMERICA, AS REPRESENTED BY THE SE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:MILLER, GERALD FRANCIS;REEL/FRAME:045199/0129 Effective date: 20180131 Owner name: UNITED STATES OF AMERICA, AS REPRESENTED BY THE SECRETARY OF THE NAVY, VIRGINIA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:MILLER, GERALD FRANCIS;REEL/FRAME:045199/0129 Effective date: 20180131 |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: APPLICATION DISPATCHED FROM PREEXAM, NOT YET DOCKETED |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: DOCKETED NEW CASE - READY FOR EXAMINATION |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: RESPONSE TO NON-FINAL OFFICE ACTION ENTERED AND FORWARDED TO EXAMINER |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: NOTICE OF ALLOWANCE MAILED -- APPLICATION RECEIVED IN OFFICE OF PUBLICATIONS |
|
STPP | Information on status: patent application and granting procedure in general |
Free format text: PUBLICATIONS -- ISSUE FEE PAYMENT VERIFIED |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
FEPP | Fee payment procedure |
Free format text: SURCHARGE FOR LATE PAYMENT, LARGE ENTITY (ORIGINAL EVENT CODE: M1554); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
MAFP | Maintenance fee payment |
Free format text: PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY Year of fee payment: 4 |